EP0749177A1 - Réflecteurs d'antenne pour une véhicule spatial et système pour les stockés et retenués - Google Patents

Réflecteurs d'antenne pour une véhicule spatial et système pour les stockés et retenués Download PDF

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Publication number
EP0749177A1
EP0749177A1 EP96301075A EP96301075A EP0749177A1 EP 0749177 A1 EP0749177 A1 EP 0749177A1 EP 96301075 A EP96301075 A EP 96301075A EP 96301075 A EP96301075 A EP 96301075A EP 0749177 A1 EP0749177 A1 EP 0749177A1
Authority
EP
European Patent Office
Prior art keywords
reflector
flexible
panel
rigid
antenna
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP96301075A
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German (de)
English (en)
Other versions
EP0749177B1 (fr
Inventor
George T. Hayes
Louise B. Brydon
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Maxar Space LLC
Original Assignee
Space Systems Loral LLC
Loral Space Systems Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Space Systems Loral LLC, Loral Space Systems Inc filed Critical Space Systems Loral LLC
Publication of EP0749177A1 publication Critical patent/EP0749177A1/fr
Application granted granted Critical
Publication of EP0749177B1 publication Critical patent/EP0749177B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
    • H01Q15/14—Reflecting surfaces; Equivalent structures
    • H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
    • H01Q15/161—Collapsible reflectors
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S343/00—Communications: radio wave antennas
    • Y10S343/02—Satellite-mounted antenna

Definitions

  • the invention generally relates to satellite reflectors of the type launched into space enclosed within a vehicle housing or fairing and deployable therefrom to be sustained in space, typically about Earth's orbit or for deep space probe applications. Specifically, the invention relates to large, compactable, furlable solid surface reflectors for reflecting electromagnetic signals.
  • High-gain antenna reflectors have been deployed into space from launch vehicles for several decades.
  • the configurations of such reflectors have varied widely as material science developed and as the sophistication of technology and scientific needs increased.
  • rigid antenna reflectors have been constructed from carbon fiber-reinforced plastic materials (CFRP). Such material can satisfy the requirements for space technology, contour accuracy and high performance antenna systems.
  • CFRP carbon fiber-reinforced plastic materials
  • performance of such antenna has been limited, owing to the size of the payload space in a carrier space vehicle.
  • Very large completely rigid antenna are highly impractical to launch into space, hence until the present, requirements for practical purposes could be satisfied only when the antenna was of a collapsible and foldable construction.
  • U.S. Patents 4,092,453 and 4,635,071 which disclose such fabrics.
  • a lightweight antenna reflector comprising a reflector panel having a parabolic surface for reflecting electromagnetic signals, said panel comprising a normally flexible composite fiber-reinforced thin outer layer and having a rigid lightweight central reinforcing core bonded to the rear surface thereof, said rigid core having a high accuracy, fixed-curvature surface and having a dimension smaller than the outer dimension of the reflector panel whereby an outer annulus of the reflector panel, comprising the normally-flexible thin outer layer thereof, extends beyond the rigid core as a flexible annulus of the reflector panel while the central areas of said normally-flexible thin outer layer are reinforced and rendered rigid by said rigid reinforcing core to provide a high accuracy fixed curvature central reflective surface.
  • a lightweight antenna reflector comprising a rigid lightweight reinforcing core having a fixed, high accuracy surface curvature and having bonded to said surface a central area of a flexible reflector panel of a composite fabric having high microwave reflecting properties, said reflector panel extending outwardly in all directions beyond said rigid core to provide an enlarged reflector panel having a flexible annulus, beyond said core, which can be folded to render the reflector more compact when not deployed for use.
  • a communications spacecraft antenna reflector stowage and restraint assembly comprising a communications spacecraft body and at least one antenna reflector member hingedly-attached to said spacecraft body for movement between compact stowage position, in which it is adjacent a face of the spacecraft body and wrapped there around, and deployed position in which it extended perpendicularly relative to said face, said antenna reflector member comprising a flexible composite fabric reflector panel having a diameter greater than the width of the face of the spacecraft body bonded to a central rigid support structure having a high accuracy surface, and hinge means between said support structure and said spacecraft body for pivoting the reflector member between said stowage and deployed positions; means for biasing said reflector member into normal deployed position, and releasable means for restraining said antenna reflector member in compact stowage position wrapped around the spacecraft body for stowage within a launch vehicle housing.
  • the novel dual band antenna assemblies of the present invention comprise at least one dual band reflector having overall L-band reflective properties and having a central, stiffened Ku-band reflective area having high reflector surface accuracy surrounded by a flexible wide annular area having L-band reflective properties, the reflector having a support hingedly attached to a spacecraft body for deployment between a stowage position, in which it is pivoted substantially parallel to the axis of the spacecraft body, and restrained up against a face of the spacecraft body with the flexible wide annular area partially flexed or curled there around, and a deployed position in which it is extended substantially perpendicular to the axis of the spacecraft body and free of restraint so that the flexible reflector element(s) is enabled to relax and return to extended, parabolic condition.
  • the stowage and restraint system preferably comprises at least one flexible retention strap supported to be wrapped around the antenna assembly to hold the reflector(s) in flexed or biased condition in stowage position, and adapted to be released and retracted automatically and remotely, or jettisoned and released into space, to enable the reflector(s) to move or be moved into deployed position and relax and flex back into parabolic condition.
  • a suitable retention strap assembly is one similar to a seat belt assembly used in automobiles, comprising a spring-loaded retraction mount and a remotely releasable latch for releasing an engagement means on the leading end of the flexible retention strap and enabling the strap to be retracted automatically to release the reflector(s) for movement into perpendicular, deployed position in which they relax and flex back into parabolic shape.
  • the spacecraft reflector antenna assembly 10 of the present invention shown in deployed condition in Fig. 1, comprises a supporting spacecraft body 11 having hingedly-attached thereto an opposed pair of circular reflector members 12 having microwave-reflective surfaces 13 which are parabolic in cross-section, members 11 being biased into deployed position in which they extend substantially perpendicular to the sides 14 of the support body 11 when released from restrained condition.
  • Each novel reflector member 12 comprises a support frame 15 bonded to the rear surface of the stiffened center section 16 of the reflector disk or panel 17, section 16 being surrounded by a flexible outer annular section 18 which is capable of being flexed in the direction of the reflecting surface into stowage position 19, illustrated by broken lines in Fig. 3, and which has memory properties which cause it to return automatically to extended relaxed position 20, also shown in Fig. 3, when the restraint is released.
  • the support frame 15 has extension legs 21, the ends of which are pivotably attached to the spacecraft body 11 by means of any well known and suitable type of hinge means 21a such as spring-biased hinge means which urge the reflector member(s) into extended position when the restraint is released.
  • the frame 15 preferably is formed as a graphite microporous or honeycomb structure to provide a strong and lightweight structure having very low thermal expansion properties. Any light weight material (usually synthetic) having a very low coefficient of expansion may be used. Such synthetic materials may be formed using any well known manufacturing technique, but molding by means of foam molds has been found to produce excellent results.
  • the reflector members 12 more precisely the reflector dishes or panels 17 thereof, comprise the stiffened high accuracy fixed curvature Ku-band reflective center section 13a and the flexible annular L-band reflective outer section 13b.
  • the center section 16 comprises a lightweight rigid or semi-rigid microporous or honeycomb stiffening structure 22 of metal or plastic material having low thermal expansion properties, similar to the material of the support 15, and bonded to the support 15 which attaches it to the spacecraft body 11.
  • the dish or reflector panel 17 preferably comprises a molded laminate of inner and outer webs or fabrics of fiber - reinforced composite synthetic material having sandwiched between a central area thereof a thicker, rigid or semi-rigid lightweight porous or honeycomb core member 22 such as of aluminum or other nonferrous lightweight metal, or more preferably a microporous or honeycomb layer of molded synthetic plastic material, similar to that of the support 15.
  • the inner web 23 or skin of composite fiber-reinforced plastic material forms the parabolic reflective concave surface 13 of the reflector members 12, conforming in the parabolic inner surface of the central honeycomb core member 22, while the rear or outer web 24 of composite fiber-reinforced synthetic plastic material is deflected over the rear surface of the honeycomb member 22 to sandwich the honeycomb core 22 between the webs 23 and 24.
  • both the inner and outer webs 23 and 24 comprise conventional composite layers including lightweight woven fabrics of carbon fibers having radio frequency reflective properties, as disclosed for example in U.S. Patents 4,868,580 and 4,812,854 and in the copending USSN 08/435,718.
  • Preferred such layers comprise high multiaxially woven modulus graphite material and a resin binder system having memory.
  • high modulus is meant material of from about 80 million psi to about 120 million psi.
  • Exemplary material includes XN70 with an RS-3 resin system (polycyanate resin system), commercially available from YLA, Inc., Benicia, California.
  • An important aspect of the preferred material is that it has shape-memory to enable it to return its original, parabolic shape when released after long-term, e.g., one to two years, storage in a folded configuration.
  • the central section 16 of the molded reflector panel 17, comprising the stiffening porous or honeycomb core structure 22 has a dimension substantially smaller than the overall diameter of the circular reflector disk or panel 17 so that a flexible outer annulus 18 of the reflector panel 17 is provided.
  • the annulus 18 or outer ring portion of the reflector panel 17 comprises a laminate of the two fiber-reinforced flexible webs 23 and 24 and is stiff enough to support itself as a flexible segment of the continuous reflector surface 13. Since the panel 17 is molded from fiber-reinforced webs in the form of a parabolic dish, the flexible outer annulus 18 has memory properties which bias it back into such configuration after the annulus 18 has been deflected inwardly for a period of time and then relaxed.
  • central stiffened section 16 is to enable use in dual band antenna systems.
  • An example would be a Ku-band (14.0 GHz) and L-Band (1.4 GHz) system where higher reflector surface accuracy is required in the central reflector surface 13a, but a less accurate reflector surface 13b is acceptable around the annulus 18 of the reflector.
  • the Ku-band antenna only utilizes the central portion 13a of the reflector, while the L-band antenna utilizes the entire reflector surface.
  • Fig. 5 of the drawing shows the antenna assembly 10 of Fig. 1 in stowage condition within the payload space of a carrier space vehicle housing 25.
  • the reflector members 12 are pivoted on hinge means 21a up against the side panels 14 of the support body 11, and the peripheral portions 18a of the flexible annular section 18 of the reflector panel 13 which extend outwardly beyond the support side panels 14 are bent or curled around the upper and lower panels, 26 and 27, respectively, of the support body 11, so as to fit within the storage space within the housing 25.
  • the assembly is releasably secured in stowed condition by means of one or more retention straps 28, one end of which is secured to a spring - biased retraction member 29 fastened to the support frame 15, and the other end of which carries a ring member which is engageable by a remotely-releasable hook member 30 fastened to the other side of the support frame 15, as illustrated by Figs. 2 and 5, similar to an automotive seat belt mechanism but having an electrically releasable member 30, such as a solenoid mechanism.
  • the hook member 30 is released to permit the retention strap 28 to be retracted by member 29 and to free the reflector members 12 to be pivoted into open position, such as by means of spring-biased hinges or other conventional means.
  • the bent or folded peripheral areas 18a of the flexible reflector panels 17 return to their original shape, due to shape-memory properties, to provide very large parabolic reflector surfaces 13 having good overall L-band-reflective properties but also having excellent Ku-band reflective properties in the rigid, high accuracy central surface area 16.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Electromagnetism (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Details Of Aerials (AREA)
  • Aerials With Secondary Devices (AREA)
  • Support Of Aerials (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
EP96301075A 1995-06-16 1996-02-16 Réflecteurs d'antenne pour un véhicule spatial et système de retenue et d'arrimage de tels réflecteurs Expired - Lifetime EP0749177B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/491,502 US5644322A (en) 1995-06-16 1995-06-16 Spacecraft antenna reflectors and stowage and restraint system therefor
US491502 1995-06-16

Publications (2)

Publication Number Publication Date
EP0749177A1 true EP0749177A1 (fr) 1996-12-18
EP0749177B1 EP0749177B1 (fr) 1998-08-26

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Application Number Title Priority Date Filing Date
EP96301075A Expired - Lifetime EP0749177B1 (fr) 1995-06-16 1996-02-16 Réflecteurs d'antenne pour un véhicule spatial et système de retenue et d'arrimage de tels réflecteurs

Country Status (4)

Country Link
US (1) US5644322A (fr)
EP (1) EP0749177B1 (fr)
JP (1) JPH098544A (fr)
DE (1) DE69600560T2 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997029907A1 (fr) * 1996-02-16 1997-08-21 Mcdonnell Douglas Corporation Structure de radome multicouche et sa fabrication
FR2777118A1 (fr) * 1998-04-03 1999-10-08 Aerospatiale Reflecteur d'antenne elastiquement deformable pour engin spatial
US6219010B1 (en) * 1998-07-02 2001-04-17 Aerospatiale Societe Nationale Industrielle Elastically deformable antenna reflector for a spacecraft
EP1149763A3 (fr) * 2000-04-25 2003-05-14 Space Systems / Loral, Inc. Engin spatial avec un mécanisme double de retenue de réflecteurs pour le déploiement simultané de plusieurs réflecteurs

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6239767B1 (en) * 1996-06-18 2001-05-29 Spacehab, Inc. Universal communications system for space applications
EP1014443A4 (fr) * 1996-09-20 2001-02-07 Tdk Corp Composants electroniques passifs, elements de circuit integre et plaquette
US6047928A (en) * 1998-05-19 2000-04-11 Hughes Electronics Corporation Friction clamp restraint mechanism for springback reflectors
FR2780820B1 (fr) 1998-07-02 2000-09-08 Aerospatiale Reflecteur d'antenne elastiquement deformable pour engin spatial et engin spatial comportant un tel reflecteur
US6215453B1 (en) 1999-03-17 2001-04-10 Burt Baskette Grenell Satellite antenna enhancer and method and system for using an existing satellite dish for aiming replacement dish
US6331839B1 (en) 1999-03-17 2001-12-18 Burt Baskette Grenell Satellite antenna enhancer and method and system for using an existing satellite dish for aiming replacement dish
US6124835A (en) * 1999-07-01 2000-09-26 Trw Inc. Deployment of dual reflector systems
US6448943B1 (en) * 2001-07-06 2002-09-10 Space Systems/Loral, Inc. Antenna system having an improved antenna support structure
US6828949B2 (en) * 2002-04-29 2004-12-07 Harris Corporation Solid surface implementation for deployable reflectors
US6775046B2 (en) * 2002-11-06 2004-08-10 Northrop Grumman Corporation Thin film shape memory alloy reflector
EP1812992B1 (fr) * 2004-11-04 2008-04-30 Spacecom Holding APS Ensemble antenne et procede de poursuite de satellite
EP1835565A1 (fr) * 2006-03-16 2007-09-19 Saab AB Reflecteur
US7965255B2 (en) * 2007-05-24 2011-06-21 Asc Signal Corporation Rotatable antenna mount
US20090058061A1 (en) * 2007-08-30 2009-03-05 Fuisz Richard C System for providing an indication indicative of whether or not a seat belt of a vehicle occupant is fastened
US9281569B2 (en) 2009-01-29 2016-03-08 Composite Technology Development, Inc. Deployable reflector
US8259033B2 (en) * 2009-01-29 2012-09-04 Composite Technology Development, Inc. Furlable shape-memory spacecraft reflector with offset feed and a method for packaging and managing the deployment of same
WO2013013122A1 (fr) * 2011-07-21 2013-01-24 Pro Brand International, Inc. Fixation par enclenchement pour montage de réflecteur
US10773833B1 (en) 2011-08-30 2020-09-15 MMA Design, LLC Panel for use in a deployable and cantilevered solar array structure
US9331394B2 (en) 2011-09-21 2016-05-03 Harris Corporation Reflector systems having stowable rigid panels
US10263316B2 (en) 2013-09-06 2019-04-16 MMA Design, LLC Deployable reflectarray antenna structure
FR3015130B1 (fr) * 2013-12-17 2016-01-22 Astrium Sas Structure segmentee, en particulier pour reflecteur d'antenne de satellite, pourvue d'au moins un dispositif de deploiement a parallelogramme
US10283835B2 (en) 2015-09-25 2019-05-07 MMA Design, LLC Deployable structure for use in establishing a reflectarray antenna
US10053240B1 (en) 2016-05-20 2018-08-21 Space Systems/Loral, Llc Stowage, deployment and positioning of rigid antenna reflectors on a spacecraft
US10730643B1 (en) 2016-09-08 2020-08-04 Space Systems/Loral, Llc Space based robotic assembly of a modular reflector
US10661918B2 (en) 2016-10-04 2020-05-26 Space Systems/Loral, Llc Self-assembling persistent space platform
US10957986B2 (en) 2017-08-04 2021-03-23 Space Systems/Loral, Llc Reconfigurable spacecraft with a hold-down assembly for a rigid reflector
US10994468B2 (en) 2018-04-11 2021-05-04 Clemson University Research Foundation Foldable composite structures
US10811759B2 (en) 2018-11-13 2020-10-20 Eagle Technology, Llc Mesh antenna reflector with deployable perimeter
US11139549B2 (en) 2019-01-16 2021-10-05 Eagle Technology, Llc Compact storable extendible member reflector
EP3912224A4 (fr) 2019-01-18 2022-10-05 M.M.A. Design, LLC Système déployable à membrane souple
US11942687B2 (en) 2019-02-25 2024-03-26 Eagle Technology, Llc Deployable reflectors
US10797400B1 (en) 2019-03-14 2020-10-06 Eagle Technology, Llc High compaction ratio reflector antenna with offset optics
RU201366U1 (ru) * 2020-02-04 2020-12-11 Александр Витальевич Лопатин Параболический трансформируемый торовый рефлектор
US11990665B2 (en) 2021-08-04 2024-05-21 M.M.A. Design, LLC Multi-direction deployable antenna
CN114243260B (zh) * 2021-12-07 2024-02-06 北京卫星制造厂有限公司 一种航天器天线反射器及制备方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4780726A (en) * 1984-12-03 1988-10-25 Trw Inc. Depolyable reflector
EP0534110A1 (fr) * 1991-09-27 1993-03-31 Hughes Aircraft Company Réflecteur d'antenne simplifié pour véhicule spatial stockable dans un conditionnement réduit

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3605107A (en) * 1969-07-17 1971-09-14 Hughes Aircraft Co Lightweight reflecting structures utilizing magnetic deployment forces
FR2517626A1 (fr) * 1981-12-04 1983-06-10 Europ Agence Spatiale Engin spatial orbital, notamment satellite, a missions multiples

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4780726A (en) * 1984-12-03 1988-10-25 Trw Inc. Depolyable reflector
EP0534110A1 (fr) * 1991-09-27 1993-03-31 Hughes Aircraft Company Réflecteur d'antenne simplifié pour véhicule spatial stockable dans un conditionnement réduit

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997029907A1 (fr) * 1996-02-16 1997-08-21 Mcdonnell Douglas Corporation Structure de radome multicouche et sa fabrication
US5707723A (en) * 1996-02-16 1998-01-13 Mcdonnell Douglas Technologies, Inc. Multilayer radome structure and its fabrication
US5849234A (en) * 1996-02-16 1998-12-15 Mcdonnell Douglas Technologies, Inc. Multilayer radome structure and its fabrication
FR2777118A1 (fr) * 1998-04-03 1999-10-08 Aerospatiale Reflecteur d'antenne elastiquement deformable pour engin spatial
US6175341B1 (en) 1998-04-03 2001-01-16 Aerospatiale Societe Nationale Industrielle Elastically deformable antenna reflector for a spacecraft
US6219010B1 (en) * 1998-07-02 2001-04-17 Aerospatiale Societe Nationale Industrielle Elastically deformable antenna reflector for a spacecraft
EP1149763A3 (fr) * 2000-04-25 2003-05-14 Space Systems / Loral, Inc. Engin spatial avec un mécanisme double de retenue de réflecteurs pour le déploiement simultané de plusieurs réflecteurs

Also Published As

Publication number Publication date
DE69600560D1 (de) 1998-10-01
JPH098544A (ja) 1997-01-10
DE69600560T2 (de) 1999-02-11
EP0749177B1 (fr) 1998-08-26
US5644322A (en) 1997-07-01

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